NO812832L - DEVICE FOR PROJECTILE WITH DRIVE ARB AT THE TIP. - Google Patents
DEVICE FOR PROJECTILE WITH DRIVE ARB AT THE TIP.Info
- Publication number
- NO812832L NO812832L NO812832A NO812832A NO812832L NO 812832 L NO812832 L NO 812832L NO 812832 A NO812832 A NO 812832A NO 812832 A NO812832 A NO 812832A NO 812832 L NO812832 L NO 812832L
- Authority
- NO
- Norway
- Prior art keywords
- tip
- projectile
- penetrator
- area
- binding means
- Prior art date
Links
- 230000007704 transition Effects 0.000 claims description 6
- 239000003380 propellant Substances 0.000 claims description 5
- 230000005484 gravity Effects 0.000 claims 1
- 230000006978 adaptation Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910001385 heavy metal Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/04—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
- F42B12/06—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with hard or heavy core; Kinetic energy penetrators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
- F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
- F42B14/061—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
- F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor
- F42B14/061—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile
- F42B14/062—Sabots for long rod fin stabilised kinetic energy projectiles, i.e. multisegment sabots attached midway on the projectile characterised by contact surfaces between projectile and sabot
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Portable Nailing Machines And Staplers (AREA)
- Surgical Instruments (AREA)
- Radar Systems Or Details Thereof (AREA)
Description
Oppfinnelsen angår en anordning v ed"" k r a f tp rosj eTTtTiT* som beskrevet i innledningen til krav 1. The invention relates to a device with "" k r a f tp rosj eTTtTiT* as described in the introduction to claim 1.
En anordning av den nevnte art er gjenstand for en parallell ansøkning med nr. 79.2738. Ved den skal det dis-ponible rom for en driv.ladning la seg forstørre på en slik måte at det av en tilsvarende større drivladning kan oppnås en øket sluttballistisk ytelse. Ved flygeprosjektilet ifølge den nevnte ansøkning ble fastslått at dets gjennomslagskraft er større ved enkeltmål enn ved flerdobbelte mål. A device of the aforementioned type is the subject of a parallel application with no. 79.2738. With it, the available space for a propellant charge can be enlarged in such a way that an increased final ballistic performance can be achieved from a correspondingly larger propellant charge. In the case of the flying projectile according to the aforementioned application, it was determined that its impact is greater with single targets than with multiple targets.
Til grunn for oppfinnelsen ligger den oppgave forThe invention is based on the task for which it is based
en anordning ved kraftprosjektil av den til å begynne med beskrevne art å forbedre gjennomslagskraften for flygeprosjektilet mot flerdobbelte mål - også ved vanskeliggjørende betingelser - og for dette formål å utforme flygeprosjektilet i området for spissen brytbar på tilsiktet måte og derved bringe mest mulig av den foreliggende inntrengningsmasse til gjennomgang gjennom målet. a device for a power projectile of the kind initially described to improve the impact force of the flying projectile against multiple targets - also in difficult conditions - and for this purpose to design the flying projectile in the area of the tip to be breakable in an intentional way and thereby bring as much as possible of the available penetration mass for review through the target.
Denne oppgave løses ved hjelp av den oppfinnelse som er angitt i karakteristikken til krav 1. Den gjør det mulig å realisere på en fordelaktig måte ikke bare den økte ytelse ved hjelp av en forstørret ladning helt måleffektivt, men også en forlengelse av den bakre del som sammen med en høy slankhetsgrad av penetratoren,som har vist seg å være gunstig, forener fordelene med tilsiktet brytbarhet og respektive størst mulige sammenhengende disponibel masse ved gjennomslag av flerdobbelte mål. Videre blir ved den på forhånd fastleggbare medvirkning av overgangskonusen i forbindelsessonen på en fordelaktig måte oppnådd en økt utskytningsfasthet for penetratoren. This task is solved with the help of the invention stated in the characteristic of claim 1. It makes it possible to realize in an advantageous way not only the increased performance by means of an enlarged charge completely target-efficient, but also an extension of the rear part which together with a high degree of slenderness of the penetrator, which has been shown to be beneficial, combines the advantages of intentional breakability and respective greatest possible continuous disposable mass when penetrating multiple targets. Furthermore, due to the predeterminable involvement of the transition cone in the connection zone, an increased launch resistance for the penetrator is advantageously achieved.
Oppfinnelsen skal i det følgende beskrives nærmere under henvisning til den på tegningen skjematisk og med av-kall på detaljer som er uvesentlige for oppfinnelsen viste foretrukne utførelse, idet figuren på tegningen viser en anordning ved kraftprosjektil ifølge oppfinnelsen med et drivbur med tre segmenter - hvilket drivbur er akseparallelt gjennomskåret i sideriss med en bare delvis fremstilt hovedpenetrator (inntrengningslegeme). In the following, the invention will be described in more detail with reference to the preferred embodiment shown schematically in the drawing and with the omission of details that are immaterial to the invention, the figure in the drawing showing a device for a power projectile according to the invention with a drive cage with three segments - which drive cage is cut parallel to the axis in side view with an only partially produced main penetrator (penetrator body).
Et løsbart drivbur 30 med tre ikke nærmere betegn^ede segmenter, hvorav et er vist i sideriss og et i snitt, har en enkelt flens 34. I området for dennes omkretsflate 32 er anordnet et tetnings- og føringsbånd 50. En gasstrykk-opptaksflate 36 som begrenser drivburet 30 bakover, strekker seg mellom den forreste ytterkant 38 og en bakre kant 40. I et område av innersiden som vender mot flygeprosjektilet 10 og ikke er nærmere betegnet, har drivburet 30 formbindingsorganer som ikke er nærmere betegnet og som tilsva-rer ujevnhetene 22.1, Derav fremkommer en forbind-élsessone 14 med en grense 16 på spissens side i nærheten av en luftlomme 46 som er avgrenset på forsiden av en forreste kant 44. I det bakre område blir den ikke nærmere be-tegnede omkretsflate av overgangskonusen 24 tett omsluttet av en respektive innvendig flate 52 på drivburet. Den indre flate 52 ender i en sirkelringkant 18 som skal beskrives i det følgende og begrenser forbindelsessonen 40 bakover. Ifølge den skjematiske fremstilling har hvert av drivbur-segmentene på baksiden en støtteutligger 48 som strekker seg radialt mot en ikke vist indre flate av røret. Ved hjelp av sistnevnte sikres på en fordelaktig måte at ved gjennomgang av kraftprosjektilanordningen gjennom utskytningsløpet vir-ker også i det bakre område av drivburet 30 en tilstrekkelig stor trykkraft radialt innover og således oppstår i samvirke med den indre flate 52 og overgangskonusen 2 4 også her en formbinding. Sirkelringkanten 18 danner således den bakre grense for forbindelsessonen 14, idet det ved hjelp av den viste anordning på en fordelaktig måte oppnås en økt utskytningsfasthet, hvilken tar hensyn til både penetrator-materialets store tetthet (fortrinnsvis en tungtmetåll-sinterlegering på basis av wolfram eller også utarmet uran)-, men også til den store lengde på baksiden av penetratoren. Til fordelen ved tilsiktet brytbarhet av forpenetratoren knytter seg den store anslagfasthet hos det gjenværende flygeprosjektil, slik at etter gjennomgangen gjennom en siste pansret del er ennå en tilstrekkelig masse disponibel ved tilsvarende kinetisk energi mot hovedpansringen. A detachable drive cage 30 with three unspecified segments, one of which is shown in side view and one in section, has a single flange 34. In the area of its peripheral surface 32, a sealing and guide band 50 is arranged. A gas pressure receiving surface 36 which limits the drive cage 30 backwards, extends between the front outer edge 38 and a rear edge 40. In an area of the inner side that faces the flying projectile 10 and is not specified in more detail, the drive cage 30 has form binding means that are not specified in more detail and which correspond to the unevenness 22.1, This results in a connection zone 14 with a boundary 16 on the side of the tip in the vicinity of an air pocket 46 which is delimited on the front side by a front edge 44. In the rear area, the not further designated circumferential surface of the transition cone 24 is tightly enclosed of a respective internal surface 52 on the drive cage. The inner surface 52 ends in a circular ring edge 18 which will be described below and limits the connection zone 40 backwards. According to the schematic representation, each of the drive cage segments has a support cantilever 48 on the back which extends radially towards an inner surface of the pipe, not shown. With the help of the latter, it is ensured in an advantageous way that when the power projectile device passes through the launching barrel, a sufficiently large compressive force also acts in the rear area of the drive cage 30 radially inward and thus occurs in cooperation with the inner surface 52 and the transition cone 2 4 also here a shape binding. The circular ring edge 18 thus forms the rear boundary of the connection zone 14, as with the aid of the device shown an increased launch resistance is advantageously achieved, which takes into account both the great density of the penetrator material (preferably a heavy metal sintered alloy based on tungsten or also depleted uranium)-, but also to the great length on the back of the penetrator. The advantage of the intended breakability of the pre-penetrator is linked to the high impact strength of the remaining flying projectile, so that after passing through the last armored part, a sufficient mass is still available at a corresponding kinetic energy against the main armour.
Det frie rom som strekke-r-=seg---efa«den'-lfoxresle f ytterkant 38 av gasstrykk-opptaksflaten 36 bakover, står til disposisjon for en sammenligningsvis betydelig forstørret drivladning. I samvirke méd dette er det mulig ved en økt sluttballistisk ytelse ved mulig forekommende modifikasjoner i Området for ujevnhetene og penetratoravsnittene samt overgangskonusen respektive i samvirke med det tilsvarende område av drivburet, å virkeliggjøre en tilpasning av kraftprosjektilanordningen ifølge oppfinnelsen til krav på mål-siden innenfor vide grenser. The free space which stretches the outer edge 38 of the gas pressure receiving surface 36 backwards is available for a comparatively significantly enlarged propellant charge. In cooperation with this, it is possible, through an increased final ballistic performance due to possible modifications in the area of the unevenness and the penetrator sections as well as the transition cone, respectively in cooperation with the corresponding area of the propellant cage, to realize an adaptation of the power projectile device according to the invention to requirements on the target side within wide borders.
Claims (2)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19803031722 DE3031722A1 (en) | 1980-08-23 | 1980-08-23 | BALANCE SHOOTING ARRANGEMENT WITH TOP-SIDED DRIVE CAGE |
Publications (1)
Publication Number | Publication Date |
---|---|
NO812832L true NO812832L (en) | 1988-02-09 |
Family
ID=6110205
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
NO812832A NO812832L (en) | 1980-08-23 | 1981-08-21 | DEVICE FOR PROJECTILE WITH DRIVE ARB AT THE TIP. |
Country Status (6)
Country | Link |
---|---|
DE (1) | DE3031722A1 (en) |
FR (1) | FR2543287B2 (en) |
GB (1) | GB2212251B (en) |
IT (1) | IT1171440B (en) |
NL (1) | NL8103810A (en) |
NO (1) | NO812832L (en) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2606868B1 (en) * | 1980-09-23 | 1989-06-23 | France Etat Armement | PERFORATING PROJECTILE WITH FRAGILIZED PERFORATING HEAD |
DE3508053A1 (en) * | 1985-03-07 | 1986-09-18 | Rheinmetall GmbH, 4000 Düsseldorf | BULLET STOCK |
DE3723909C2 (en) * | 1987-07-18 | 1994-12-08 | Rheinmetall Gmbh | Penetrator |
DE3724401A1 (en) * | 1987-07-23 | 1989-05-18 | Rheinmetall Gmbh | Wing-stabilized, sub-caliber floating cage |
DE3843503A1 (en) * | 1988-12-23 | 1992-05-27 | Rheinmetall Gmbh | Armour piercing missile assembly - has front and rear missile segmented propulsion cages detachably secured to each other |
DE3911575A1 (en) * | 1989-04-08 | 1990-10-11 | Rheinmetall Gmbh | FLOOR ARRANGEMENT |
DE3930255A1 (en) * | 1989-09-11 | 1991-03-21 | Rheinmetall Gmbh | Countering transverse vibration of slender penetrator with sabot - by terminal projecting struts abutting missile wall |
DE4012154A1 (en) * | 1990-04-14 | 1991-10-17 | Rheinmetall Gmbh | SUB-CALIBRARY FLOOR WITH DRIVE CAGE |
DE4022821A1 (en) * | 1990-07-18 | 1992-01-23 | Rheinmetall Gmbh | sub-calibre armour-piercing projectile - with single frangible region between front and main penetrator cores |
FR2673278B1 (en) * | 1991-02-26 | 1993-12-31 | Giat Industries | FRAGMENTABLE PERFORATING SUB-CALIBER PROJECTILE. |
DE102019135870A1 (en) * | 2019-12-30 | 2021-07-01 | Ruag Ammotec Ag | Projectile and ammunition |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB594517A (en) * | 1940-09-04 | 1947-11-13 | Charles Dennistoun Burney | Improvements in or relating to aeroplane and other bombs or projectiles |
US2996011A (en) * | 1944-06-30 | 1961-08-15 | Henry F Dunlap | Projectile |
US2968246A (en) * | 1944-06-30 | 1961-01-17 | Henry F Dunlap | Projectile |
US3148472A (en) * | 1962-06-11 | 1964-09-15 | Edward N Hegge | Subcaliber projectile and sabot for high velocity firearms |
US3262391A (en) * | 1964-10-12 | 1966-07-26 | Budd Co | Subcaliber projectile and sabot |
DE1428679C1 (en) * | 1964-12-29 | 1977-09-15 | Deutsch Franz Forsch Inst | Hard core bullet for fighting tank targets |
CH478397A (en) * | 1968-06-01 | 1969-09-15 | Rheinmetall Gmbh | Practice floor |
SE377840B (en) * | 1972-04-20 | 1975-07-28 | Ladco Enterprises Ltd | |
US4085678A (en) * | 1977-04-25 | 1978-04-25 | The United States Of America As Represented By The Secretary Of The Air Force | Kinetic energy, impact-separated, follow-through ungula penetrator |
DE2836963A1 (en) * | 1978-08-24 | 1984-03-08 | Rheinmetall GmbH, 4000 Düsseldorf | AMMUNITION UNIT FOR TUBE ARMS |
-
1980
- 1980-08-23 DE DE19803031722 patent/DE3031722A1/en active Granted
-
1981
- 1981-08-07 IT IT49070/81A patent/IT1171440B/en active
- 1981-08-13 NL NL8103810A patent/NL8103810A/en not_active Application Discontinuation
- 1981-08-19 GB GB8125293A patent/GB2212251B/en not_active Expired - Lifetime
- 1981-08-20 FR FR8115984A patent/FR2543287B2/en not_active Expired
- 1981-08-21 NO NO812832A patent/NO812832L/en unknown
Also Published As
Publication number | Publication date |
---|---|
FR2543287A2 (en) | 1984-09-28 |
NL8103810A (en) | 1984-06-01 |
FR2543287B2 (en) | 1986-09-12 |
GB2212251A (en) | 1989-07-19 |
IT1171440B (en) | 1987-06-10 |
GB2212251B (en) | 1990-02-28 |
DE3031722A1 (en) | 1986-10-09 |
DE3031722C2 (en) | 1988-06-23 |
IT8149070A0 (en) | 1981-08-07 |
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